Airfoil having internal hybrid cooling cavities

ABSTRACT

Airfoils bodies having a first core cavity and a second core cavity located within the airfoil body that is adjacent the first core cavity. The second core cavity is defined by a first cavity wall, a second cavity wall, a first exterior wall, and a second exterior wall, wherein the first cavity wall is located between the second core cavity and the first core cavity and the first and second exterior walls are exterior walls of the airfoil body. The first cavity wall includes a first surface angled toward the first exterior wall and a second surface angled toward the second exterior wall. At least one first cavity impingement hole is formed within the first surface and a central ridge extends into the second core cavity from at least one of the first cavity wall and the second wall and divides the second core cavity into a two-vortex chamber.

BACKGROUND

Illustrative embodiments pertain to the art of turbomachinery, andspecifically to turbine rotor components.

Gas turbine engines are rotary-type combustion turbine engines builtaround a power core made up of a compressor, combustor and turbine,arranged in flow series with an upstream inlet and downstream exhaust.The compressor compresses air from the inlet, which is mixed with fuelin the combustor and ignited to generate hot combustion gas. The turbineextracts energy from the expanding combustion gas, and drives thecompressor via a common shaft. Energy is delivered in the form ofrotational energy in the shaft, reactive thrust from the exhaust, orboth.

The individual compressor and turbine sections in each spool aresubdivided into a number of stages, which are formed of alternating rowsof rotor blade and stator vane airfoils. The airfoils are shaped toturn, accelerate and compress the working fluid flow, or to generatelift for conversion to rotational energy in the turbine.

Airfoils may incorporate various cooling cavities located adjacentexternal side walls. Such cooling cavities are subject to both hotmaterial walls (exterior or external) and cold material walls (interioror internal). Although such cavities are designed for cooling portionsof airfoil bodies, various cooling flow characteristics can cause hotsections where cooling may not be sufficient. Accordingly, improvedmeans for providing cooling within an airfoil may be desirable.

BRIEF DESCRIPTION

According to some embodiments, airfoils for gas turbine engines areprovided. The airfoils include an airfoil body having a plurality ofcavities formed therein, the airfoil extending in a radial directionbetween a first end and a second end, and extending axially between aleading edge and a trailing edge, a first core cavity within the airfoilbody, and a second core cavity located within the airfoil body andadjacent the first core cavity, wherein the second core cavity isdefined by a first cavity wall, a second cavity wall opposing the firstcavity wall, a first exterior wall, and a second exterior wall opposingthe first exterior wall, wherein the first cavity wall is locatedbetween the second core cavity and the first core cavity and the firstand second exterior walls are exterior walls of the airfoil body. Thefirst cavity wall includes a first surface angled toward the firstexterior wall and a second surface angled toward the second exteriorwall and at least one first cavity impingement hole is formed within thefirst surface, wherein a first impingement flow flows from the firstcore cavity through the at least one first cavity impingement hole andimpinges upon the first exterior wall to form a first high momentum jetof impingement air thereon and a central ridge extending into the secondcore cavity from at least one of the first cavity wall and the secondwall, wherein the central ridge at least partially divides the secondcore cavity into a two-vortex chamber.

In addition to one or more of the features described herein, or as analternative, further embodiments of the airfoils may include that thecentral ridge is a forward central ridge extending into the second corecavity from the first cavity wall, the airfoil further comprising an aftcentral ridge extending into the second core cavity from the secondcavity wall.

In addition to one or more of the features described herein, or as analternative, further embodiments of the airfoils may include at leastone second cavity impingement hole formed within the second surface,wherein a second impingement flow flows from the first core cavitythrough the at least one second cavity impingement hole and impingesupon the second exterior wall to form a second high momentum jetthereon.

In addition to one or more of the features described herein, or as analternative, further embodiments of the airfoils may include that thefirst impingement flow separates into the first high momentum jetflowing along the first exterior wall and a first portion of a radialcooling flow within the second core cavity and the second impingementflow separates into the second high momentum jet flowing along thesecond exterior wall and a second portion of the radial cooling flowwithin the second core cavity, wherein the first and second portions ofthe radial cooling flow flow radially within the two-vortex chamber.

In addition to one or more of the features described herein, or as analternative, further embodiments of the airfoils may include at leastone circuit exit in the first exterior wall, the at least one circuitexit arranged to expel air from the second core cavity through the firstexterior wall.

In addition to one or more of the features described herein, or as analternative, further embodiments of the airfoils may include a funnelingfeature extending the second core cavity along the first exterior wallto the at least one circuit exit.

In addition to one or more of the features described herein, or as analternative, further embodiments of the airfoils may include at leastone heat transfer augmentation feature within the at least one circuitexit.

In addition to one or more of the features described herein, or as analternative, further embodiments of the airfoils may include at leastone film exit in the first exterior wall, the at least one film exitarranged to expel air from the second core cavity through the firstexterior wall.

In addition to one or more of the features described herein, or as analternative, further embodiments of the airfoils may include a funnelingfeature extending the second core cavity along the first exterior wallto the at least one circuit exit.

In addition to one or more of the features described herein, or as analternative, further embodiments of the airfoils may include that the atleast one first cavity impingement hole has one of a radial orientation,an axial orientation, or an angular orientation within the first cavitywall.

According to some embodiments, core structures for manufacturingairfoils for gas turbine engines are provided. The core structuresinclude a first core cavity core to form a first core cavity and asecond core cavity core to form a second core cavity, the second corecavity core located adjacent the first core cavity core, wherein thesecond core cavity core is arranged to form a first cavity wall, asecond cavity wall opposing the first cavity wall, a first exteriorwall, and a second exterior wall opposing the first exterior wall in aformed airfoil body such that the first cavity wall is located betweenthe second core cavity core and the first core cavity and the first andsecond exterior walls are exterior walls of the formed airfoil body. Aspace between the first core cavity core and the second core cavity corethat defines the first cavity wall includes a first portion to form afirst surface of the first cavity wall that is angled toward the formedfirst exterior wall and a second portion to form a second surface of thefirst cavity wall that is angled toward the formed second exterior wall.At least one first cavity impingement stem extends between the firstcore cavity core and the second core cavity core, wherein at least onefirst cavity impingement hole is formed thereby in a formed airfoil bodysuch that cooling flow can flow from the first core cavity through theat least one first cavity impingement hole and impinge upon the firstexterior wall of the formed airfoil body to form a first high momentumjet of impingement air thereon. A central channel is formed in thesecond core cavity core extending into the second core cavity core toform a central ridge on at least one of the first cavity wall and thesecond cavity wall, wherein the central ridge at least partially dividesthe second core cavity into a two-vortex chamber.

In addition to one or more of the features described herein, or as analternative, further embodiments of the core structures may include atleast one second cavity impingement stem extending between the firstcore cavity core and the second core cavity core, wherein at least onesecond cavity impingement hole is formed thereby in a formed airfoilbody such that cooling flow can flow from the first core cavity throughthe at least one second cavity impingement hole and impinge upon thesecond exterior wall of the formed airfoil body to form a second highmomentum jet thereon.

In addition to one or more of the features described herein, or as analternative, further embodiments of the core structures may include atleast one film exit stem attached to the second core cavity core to format least one film exit in the first exterior wall, the at least one filmexit arranged to expel air from the second core cavity through the firstexterior wall in the formed airfoil body.

In addition to one or more of the features described herein, or as analternative, further embodiments of the core structures may include thatthe at least one formed film exit is arranged to pull the impingementair from the at least one first cavity impingement hole along aninterior surface of the first exterior wall within the second corecavity of the formed airfoil.

In addition to one or more of the features described herein, or as analternative, further embodiments of the core structures may include atleast one film exit core attached to the second core cavity core to format least one circuit exit in the first exterior wall, the at least onecircuit exit arranged to expel air from the second core cavity throughthe first exterior wall in the formed airfoil body.

In addition to one or more of the features described herein, or as analternative, further embodiments of the core structures may include thatthe at least one film exit core includes one or more heat transferaugmentation core features therein to form heat transfer augmentationfeatures in the at least one circuit exit.

In addition to one or more of the features described herein, or as analternative, further embodiments of the core structures may include thatthe central channel is a forward central channel extending into thesecond core cavity core to form a forward central ridge in a formedairfoil, the core structure further comprising an aft central channelextending into the second core cavity to form an aft central ridge inthe formed airfoil.

In addition to one or more of the features described herein, or as analternative, further embodiments of the core structures may include afunnel feature extension extending from the second core cavity core inan aftward direction to form a funneling feature in a formed airfoil.

In addition to one or more of the features described herein, or as analternative, further embodiments of the core structures may include thatthe at least one first cavity impingement stem is oblong in shape andhas one of a radial orientation, an axial orientation, or an angularorientation.

According to some embodiments, gas turbine engines are provided. The gasturbine engines include an airfoil having an airfoil body having aplurality of cavities formed therein, the airfoil extending in a radialdirection between a first end and a second end, and extending axiallybetween a leading edge and a trailing edge, a first core cavity withinthe airfoil body, and a second core cavity located within the airfoilbody and adjacent the first core cavity, wherein the second core cavityis defined by a first cavity wall, a second cavity wall opposing thefirst cavity wall, a first exterior wall, and a second exterior wallopposing the first exterior wall, wherein the first cavity wall islocated between the second core cavity and the first core cavity and thefirst and second exterior walls are exterior walls of the airfoil body.The first cavity wall includes a first surface angled toward the firstexterior wall and a second surface angled toward the second exteriorwall. At least one first cavity impingement hole is formed within thefirst surface, wherein a first impingement flow flows from the firstcore cavity through the at least one first cavity impingement hole andimpinges upon the first exterior wall to form a first high momentum jetof impingement air thereon. A central ridge extends into the second corecavity from at least one of the first cavity wall and the second wall,wherein the central ridge at least partially divides the second corecavity into a two-vortex chamber.

The foregoing features and elements may be combined in variouscombinations without exclusivity, unless expressly indicated otherwise.These features and elements as well as the operation thereof will becomemore apparent in light of the following description and the accompanyingdrawings. It should be understood, however, the following descriptionand drawings are intended to be illustrative and explanatory in natureand non-limiting.

BRIEF DESCRIPTION OF THE DRAWINGS

The following descriptions should not be considered limiting in any way.With reference to the accompanying drawings, like elements are numberedalike: The subject matter is particularly pointed out and distinctlyclaimed at the conclusion of the specification. The foregoing and otherfeatures, and advantages of the present disclosure are apparent from thefollowing detailed description taken in conjunction with theaccompanying drawings in which like elements may be numbered alike and:

FIG. 1 is a schematic cross-sectional illustration of a gas turbineengine;

FIG. 2 is a schematic illustration of a portion of a turbine section ofthe gas turbine engine of FIG. 1;

FIG. 3 is a schematic illustration of a hybrid cavity configuration ofan airfoil;

FIG. 4A is a schematic illustration of a cavity configuration of anairfoil in accordance with an embodiment of the present disclosure;

FIG. 4B is a schematic illustration of airflow through the airfoil ofFIG. 4A;

FIG. 5A is a top down plan view cross-section illustration of internalcavities of an airfoil in accordance with an embodiment of the presentdisclosure;

FIG. 5B is a side elevation cross-section illustrating the internalcavities of the airfoil of FIG. 5A and illustrating air flow flowingtherein;

FIG. 6 is a schematic illustration of a portion of a core structure forforming an airfoil in accordance with an embodiment of the presentdisclosure;

FIG. 7 is a schematic illustration of a cross-section of an airfoil inaccordance with an embodiment of the present disclosure;

FIG. 8 is a schematic illustration of a portion of a core structure forforming an airfoil in accordance with an embodiment of the presentdisclosure;

FIG. 9 is a schematic illustration of a cross-section of an airfoil inaccordance with an embodiment of the present disclosure;

FIG. 10 is a schematic illustration of a portion of a core structure forforming an airfoil in accordance with an embodiment of the presentdisclosure;

FIG. 11 is a schematic illustration of a cross-section of an airfoil inaccordance with an embodiment of the present disclosure;

FIG. 12 is a schematic illustration of a portion of a core structure forforming an airfoil in accordance with an embodiment of the presentdisclosure;

FIG. 13 is a schematic illustration of a portion of an airfoil inaccordance with an embodiment of the present disclosure;

FIG. 14 is a schematic illustration of a portion of an airfoil inaccordance with an embodiment of the present disclosure;

FIG. 15 is a schematic illustration of a cross-section of an airfoil inaccordance with an embodiment of the present disclosure;

FIG. 16 is a schematic illustration of a portion of a core structure forforming an airfoil in accordance with an embodiment of the presentdisclosure;

FIG. 17 is an elevation view of a cavity wall in accordance with anembodiment of the present disclosure illustrating an impingement holeconfiguration;

FIG. 18 is an elevation view of a cavity wall in accordance with anembodiment of the present disclosure illustrating an impingement holeconfiguration; and

FIG. 19 is a schematic illustration of a portion of a core structure forforming an airfoil in accordance with an embodiment of the presentdisclosure.

DETAILED DESCRIPTION

Detailed descriptions of one or more embodiments of the disclosedapparatus and/or methods are presented herein by way of exemplificationand not limitation with reference to the Figures.

FIG. 1 schematically illustrates a gas turbine engine 20. The gasturbine engine 20 is disclosed herein as a two-spool turbofan thatgenerally incorporates a fan section 22, a compressor section 24, acombustor section 26 and a turbine section 28. Alternative engines mightinclude an augmentor section (not shown) among other systems orfeatures. The fan section 22 drives air along a bypass flow path B in abypass duct, while the compressor section 24 drives air along a coreflow path C for compression and communication into the combustor section26 then expansion through the turbine section 28. Although depicted as atwo-spool turbofan gas turbine engine in the disclosed non-limitingembodiment, it should be understood that the concepts described hereinare not limited to use with two-spool turbofans as the teachings may beapplied to other types of turbine engines including three-spoolarchitectures.

The exemplary engine 20 generally includes a low speed spool 30 and ahigh speed spool 32 mounted for rotation about an engine centrallongitudinal axis A relative to an engine static structure 36 viaseveral bearing systems 38. It should be understood that various bearingsystems 38 at various locations may alternatively or additionally beprovided, and the location of bearing systems 38 may be varied asappropriate to the application.

The low speed spool 30 generally includes an inner shaft 40 thatinterconnects a fan 42, a low pressure compressor 44 and a low pressureturbine 46. The inner shaft 40 is connected to the fan 42 through aspeed change mechanism, which in exemplary gas turbine engine 20 isillustrated as a geared architecture 48 to drive the fan 42 at a lowerspeed than the low speed spool 30. The high speed spool 32 includes anouter shaft 50 that interconnects a high pressure compressor 52 and highpressure turbine 54. A combustor 56 is arranged in exemplary gas turbine20 between the high pressure compressor 52 and the high pressure turbine54. An engine static structure 36 is arranged generally between the highpressure turbine 54 and the low pressure turbine 46. The engine staticstructure 36 further supports bearing systems 38 in the turbine section28. The inner shaft 40 and the outer shaft 50 are concentric and rotatevia bearing systems 38 about the engine central longitudinal axis Awhich is collinear with their longitudinal axes.

The core airflow is compressed by the low pressure compressor 44 thenthe high pressure compressor 52, mixed and burned with fuel in thecombustor 56, then expanded over the high pressure turbine 54 and lowpressure turbine 46. The turbines 46, 54 rotationally drive therespective low speed spool 30 and high speed spool 32 in response to theexpansion. It will be appreciated that each of the positions of the fansection 22, compressor section 24, combustor section 26, turbine section28, and fan drive gear system 48 may be varied. For example, gear system48 may be located aft of combustor section 26 or even aft of turbinesection 28, and fan section 22 may be positioned forward or aft of thelocation of gear system 48.

The engine 20 in one example is a high-bypass geared aircraft engine. Ina further example, the engine 20 bypass ratio is greater than about six(6), with an example embodiment being greater than about ten (10), thegeared architecture 48 is an epicyclic gear train, such as a planetarygear system or other gear system, with a gear reduction ratio of greaterthan about 2.3 and the low pressure turbine 46 has a pressure ratio thatis greater than about five. In one disclosed embodiment, the engine 20bypass ratio is greater than about ten (10:1), the fan diameter issignificantly larger than that of the low pressure compressor 44, andthe low pressure turbine 46 has a pressure ratio that is greater thanabout five 5:1. Low pressure turbine 46 pressure ratio is pressuremeasured prior to inlet of low pressure turbine 46 as related to thepressure at the outlet of the low pressure turbine 46 prior to anexhaust nozzle. The geared architecture 48 may be an epicycle geartrain, such as a planetary gear system or other gear system, with a gearreduction ratio of greater than about 2.3:1. It should be understood,however, that the above parameters are only exemplary of one embodimentof a geared architecture engine and that the present disclosure isapplicable to other gas turbine engines including direct driveturbofans.

A significant amount of thrust is provided by the bypass flow B due tothe high bypass ratio. The fan section 22 of the engine 20 is designedfor a particular flight condition—typically cruise at about 0.8 Mach andabout 35,000 feet (10,688 meters). The flight condition of 0.8 Mach and35,000 ft (10,688 meters), with the engine at its best fuelconsumption—also known as “bucket cruise Thrust Specific FuelConsumption (‘TSFC’)”—is the industry standard parameter of lbm of fuelbeing burned divided by lbf of thrust the engine produces at thatminimum point. “Low fan pressure ratio” is the pressure ratio across thefan blade alone, without a Fan Exit Guide Vane (“FEGV”) system. The lowfan pressure ratio as disclosed herein according to one non-limitingembodiment is less than about 1.45. “Low corrected fan tip speed” is theactual fan tip speed in ft/sec divided by an industry standardtemperature correction of [(Tram ° R)/(514.7° R)]0.5. The “Low correctedfan tip speed” as disclosed herein according to one non-limitingembodiment is less than about 1150 ft/second (350.5 m/sec).

Although the gas turbine engine 20 is depicted as a turbofan, it shouldbe understood that the concepts described herein are not limited to usewith the described configuration, as the teachings may be applied toother types of engines such as, but not limited to, turbojets,turboshafts, and three-spool (plus fan) turbofans wherein anintermediate spool includes an intermediate pressure compressor (“IPC”)between a low pressure compressor (“LPC”) and a high pressure compressor(“HPC”), and an intermediate pressure turbine (“IPT”) between the highpressure turbine (“HPT”) and the low pressure turbine (“LPT”).

FIG. 2 is a schematic view of a portion of the turbine section 28 thatmay employ various embodiments disclosed herein. Turbine section 28includes a plurality of airfoils 60, 62 including, for example, one ormore blades and vanes. The airfoils 60, 62 may be hollow bodies withinternal cavities defining a number of channels or cores, hereinafterairfoil cores, formed therein and extending from an inner diameter 66 toan outer diameter 68, or vice-versa. The airfoil cores may be separatedby partitions within the airfoils 60, 62 that may extend either from theinner diameter 66 or the outer diameter 68 of the airfoil 60, 62. Thepartitions may extend for a portion of the length of the airfoil 60, 62,but may stop or end prior to forming a complete wall within the airfoil60, 62. Thus, each of the airfoil cores may be fluidly connected andform a fluid path within the respective airfoil 60, 62. The airfoils 60,62 may include platforms 70 located proximal to the inner diameter 66thereof. Located below the platforms 70 (e.g., radially inward withrespect to the engine axis) may be airflow ports and/or bleed orificesthat enable air to bleed from the internal cavities of the airfoils 60,62. A root of the airfoil may connect to or be part of the platform 70.

The turbine section 28 is housed within a case 80, which may havemultiple parts (e.g., turbine case, diffuser case, etc.). In variouslocations, components, such as seals, may be positioned between airfoils60, 62 and the case 80. For example, as shown in FIG. 2, blade outer airseals 82 (hereafter “BOAS”) are located radially outward from the blade60. As will be appreciated by those of skill in the art, the BOAS 82 mayinclude BOAS supports that are configured to fixedly connect or attachthe BOAS 82 to the case 80 (e.g., the BOAS supports may be locatedbetween the BOAS 82 and the case 80). As shown in FIG. 2, the case 80includes a plurality of case hooks 84 that engage with BOAS hooks 86 tosecure the BOAS 82 between the case 80 and a tip of the airfoil 60.

As shown and labeled in FIG. 2, a radial direction is upward on the page(e.g., radial with respect to an engine axis) and an axial direction isto the right on the page (e.g., along an engine axis). Thus, radialcooling flows will travel up or down on the page and axial flows willtravel left-to-right (or vice versa).

Turning to FIG. 3, an airfoil 300 having internal hybrid cavities isshown. As used herein, a “hybrid cavity” is an internal cavity of anairfoil that has one wall that is a hot wall (e.g., exterior surface ofan airfoil body and exposed to hot, gaspath air) and another wall thatis a cold wall (e.g., a wall that is not exposed to the hot gaspath air,and may be an internal or interior wall structure of the airfoil). Forexample, as shown in FIG. 3, the airfoil 300 has a two leading edgehybrid cavities 302, a pressure side hybrid cavity 304, and a suctionside hybrid cavity 306.

The hybrid cavities 302, 304, 306 are defined in the airfoil 300 with afirst wall of the hybrid cavity defined by an exterior surface wall 310of the airfoil 300. The exterior surface wall 310 is a “hot” wall of theairfoil 300 that is exposed to hot, gaspath air. A second wall of thehybrid cavity is defined by an interior wall 312, with the interior wall312 being a “cold” wall of the airfoil 300. A cold wall is one that isnot exposed to the hot gaspath air, and thus remains relatively cool incomparison to the hot, exterior surface walls. For example, the interiorwalls 312 can be adjacent to or part of defining walls of internal, coldcore cavities 308.

Embodiments described herein are directed to eliminating the need forthe interior wall to define the hybrid cavities. For example, in someembodiments, the elimination of the interior cold wall(s) is achieved byconnecting a first core cavity to a second core cavity with a doubleimpingement rib along the edges of the second core cavity. The doubleimpingement rib directs air from the first core cavity to the secondcore cavity along an external hot wall of the second core cavity.Further, one or more sets of film holes are arranged along the externalhot wall of the second core cavity to directionally pull the air alongthe external hot wall, thus generating a high momentum jet along aninterior surface of the external hot wall within the second core cavity.The high momentum jet within the second core cavity creates a flow fieldthat rides along the external hot wall and creates a “dead zone” in themiddle of the second core cavity. The “dead zone” is an area or regionof the second core cavity that is not directly influenced by theimpingement cooling from the first core cavity and enables a radialcooling flow to pass through the middle of the second core cavity.Advantageously, embodiments provided herein enable the benefits of ahybrid cavity without the added weight of a conventional hybrid cavitygeometry (e.g., employing the interior cold wall).

For example, turning to FIGS. 4A-4B, schematic illustrations of anairfoil 400 in accordance with an embodiment of the present disclosureshown. FIG. 4A illustrates the structure of the airfoil 400 and FIG. 4Billustrates a portion of an airflow through the airfoil 400. In thisembodiment, a leading edge 402 of the airfoil 400 is arranged with twoleading edge hybrid cavities 404. The cold walls of the leading edgehybrid cavities 404 is defined by a first core cavity 406. As shown, thefirst core cavity 406 is a typical cold, internal cavity, similar tothat shown in FIG. 3. Aft of the first core cavity 406 is a second corecavity 408. The second core cavity 408, as shown, is not a hybridcavity, but rather has two opposing exterior walls 410, 412. A firstexterior wall 410 of the second core cavity 408 is a hot wall on apressure side of the airfoil 400 and a second exterior wall 412 of thesecond core cavity 408 is a hot wall on a suction side of the airfoil400. The first core cavity 406 and the second core cavity 408 aredivided or separated by an impingement rib 414.

The impingement rib 414 includes a first set of impingement holes 416and a second set of impingement holes 418. The first and second sets ofimpingement holes 416, 418 are arranged to fluidly connect the firstcore cavity 406 to the second core cavity 408 and to direct impingementair from the first core cavity 406 into the second core cavity 408 alongthe exterior walls 410, 412. The impinging air from the first corecavity 406 into the second core cavity 408 is achieved due to a pressuredifferential between the first and second core cavities 406, 408. Thefirst core cavity 408 has relatively high air pressure therein. The highair pressure is due to a fed of cooling air supplied into the first corecavity 406, such as from a platform, inner diameter source, outerdiameter source, etc. as will be appreciated by those of skill in theart. The second core cavity 408 has relatively low air pressure, whichmay be a result of a restricted cooling flow, or an absence of asupplied cooling flow directly into the second core cavity 408. Thedifference in pressure causes the air from the first core cavity 406 toflow into the second core cavity 408 through the impingement holes 416,418. In a blade configuration, for example, the first core cavity 406may be sourced from a root region and the second core 408 may be closedoff from being sourced from the root region (e.g., completely sealed,blocked by a metering plate or other structure, etc.), thus resulting ina differential pressure between the first and second core cavities 406,408. In embodiments where the second core cavity 408 is completelysealed, all cooling air within the second core cavity 408 can be sourcedfrom the first cooling cavity 406. In a vane configuration, for example,the first and second core cavities 406, 408 could have two differentsources with two different air pressures to achieve a desireddifferential pressure to achieve the impingement from the first corecavity 406 into the second core cavity 408.

As shown in FIGS. 4A-4B, the first set of impingement holes 416 areangled to direct impingement air from the first core cavity 406 at thefirst exterior wall 410 within the second core cavity 408. Similarly,the second set of impingement holes 418 are angled to direct impingementair from the first core cavity 406 at the second exterior wall 412within the second core cavity 408. The impinging air forms a highmomentum jet of air along the interior surfaces of the exterior walls410, 412 thus isolating an internal dead zone 424, as shown anddescribed herein. The second core cavity 408 has a first film exit 420on the first exterior wall 410 that enables a portion of a flow to passfrom the second core cavity 408 to the exterior of the airfoil 400, suchas out along a pressure side wall exterior surface of the airfoil 400.The second core cavity 408, as shown, also includes a second film exit422 on the second exterior wall 412 that enables a portion of a flow topass from the second core cavity 408 to the exterior of the airfoil 400,such as out along a suction side wall exterior surface of the airfoil400.

With reference to FIG. 4B, a schematic illustration of an airflowthrough the airfoil 400 is shown. A first side cooling flow 426originates within the first core cavity 406, flows through the first setof impingement holes 416 in the impingement rib 414 into the second corecavity 408 along the first exterior wall 410. Similarly, a second sidecooling flow 428 originates within the first core cavity 406, flowsthrough the second set of impingement holes 418 in the impingement rib414 into the second core cavity 408 along the second exterior wall 412.The first side cooling flow 426 is drawn through the second core cavity408 along the first exterior wall 410 by the pull of airflow through thefirst film exit 420. Similarly, the second side cooling flow 428 isdrawn through the second core cavity 408 along the second exterior wall412 by the pull of airflow through the second film exit 422.

As shown in FIG. 4B, the first and second side cooling flows 426, 428create a dead zone 424 within the second core cavity 408. The first andsecond sets of impingement holes 416, 418 include impingement holes thatare configured to enable high velocity, high momentum side cooling flows426, 428 to be formed as a high momentum jet along the interior surfacesof the first and second exterior side walls 410, 412 of the second corecavity 408. The high velocity, high momentum jet flow of the sidecooling flows 426, 428 can isolate the dead zone 424 from the hotsurfaces of the exterior side walls 410, 412, thus preventing highthermal transfer from the material of the airfoil 400 into the dead zone424.

As shown, a radial cooling flow 430 passes through the second corecavity 408 along the interior surface of the exterior side walls 410,412. The radial cooling flow 430 may be a typical cooling flow passingfrom one end of an airfoil (or cavity) to another end of the airfoil (orcavity). The radial cooling flow 430 can flow in either direction, e.g.,radially outward toward an outer diameter or radially inward toward aninner diameter. For example, in some embodiments, the radial coolingflow 430 can flow from a root or first end of the airfoil 400 to a tipor second end of the airfoil 400. In some embodiments, the radialcooling flow 430 is entirely formed from a portion of the air flowingthrough the first and second sets of impingement holes 416, 418 (e.g.,from the first core cavity 406). In other embodiments, a portion of theradial cooling flow 430 can be sourced from a root or tip region and/orfrom other internal cavities of the airfoil (although the pressurewithin the second cavity core 408 will still be less than that withinthe first cavity core 408).

The radial cooling flow 430 may have low MACH numbers, slow flow, andlow momentum. As illustratively shown, a portion of the radial coolingflow 430 may be rotated or swirled by the flow of the side cooling flows426, 428. For example, in some arrangements, the side cooling flows 426,428 can cause dynamic vortices to be generated within the second corecavity 408, with the dynamic vortices operating to contain the sidecooling flows 426, 428 against the exterior walls 410, 412 (e.g.,compress/push the high momentum jet air of the side cooling flows 426,428 against the exterior walls 410, 412) and/or to contain and channelthe radial cooling flow 430 within the dead zone 424 of the second corecavity 408.

Turning now to FIGS. 5A-5B, schematic illustrations of an airfoil 500 inaccordance with an embodiment of the present disclosure are shown. FIG.5A is a top down plan view cross-section illustrating the internalcavities of the airfoil 500 and FIG. 5B is a side elevationcross-section illustrating the internal cavities of the airfoil 500illustrating air flow flowing therein. The airfoil 500 includes a firstcore cavity 502 and a second core cavity 504 having an arrangementsimilar to that described above, wherein side cooling flows aregenerated by airflow that flows from the first core cavity 502 alonginterior side walls of the second core cavity 504 and then is expelledout of the airfoil 500.

An interior of the airfoil 500, at a leading edge 506, is divided intomultiple leading edge hybrid cavities 508. Although shown with twoleading edge hybrid cavities 508, various embodiments may have anynumber of leading edge hybrid or non-hybrid, core cavities, including asingle leading edge cavity (hybrid or core cavity). The leading edgehybrid cavities 508 are arranged as leading-edge impingement cavitiesthat are supplied with impingement air from the first core cavity 502through one or more forward impingement holes 510. The impinging airfrom the first core cavity 502 into the leading edge hybrid cavities 508allows for changes in pressure distribution across the leading edge 506of the airfoil 500 without causing back flow margin issues. The leadingedge hybrid cavities 508 are fed from the first core cavity 502, whichmay be a leading edge feed cavity which also feeds the second corecavity 504, in a manner similar to that described above.

The second core cavity 504 is defined in an axial direction between afirst cavity wall 512 and a second cavity wall 514. In a circumferentialdirection, the second core cavity 504 is defined by a first exteriorwall 516 and an opposing second exterior wall 518. As discussed above,the exterior walls 516, 518 of the second core cavity 504 are “hot”walls that are exposed to hot gaspath air. In this embodiment, the firstcavity wall 512 and the second cavity wall 514 are “cold” walls that arenot exposed to the hot gaspath air (i.e., they are internal walls). Thefirst cavity wall 512 includes one or more cavity impingement holes 520,522. In this embodiment, a first set of cavity impingement holes 520 ispositioned and oriented within the first cavity wall 512 to direct anaft-flowing impingement flow from the first core cavity 502 into thesecond core cavity 504 and at the first exterior side wall 516.Similarly, a second set of cavity impingement holes 522 is positionedand oriented within the first cavity wall 512 to direct an aft-flowingimpingement flow from the first core cavity 502 into the second corecavity 504 and at the second exterior side wall 518.

As shown, part of the directing of the impinging flow from the firstcore cavity 502 to the second core cavity 504 is achieved by the firstcavity wall 512 being contoured or shaped. In the present embodiment,the first cavity wall 512 has a first surface 524 that is angled orfaces the first exterior wall 516. Similarly, the first cavity wall 512has a second surface 526 that is angled or faces the second exteriorwall 518. Although the first cavity wall 512 has a specific geometricshape (e.g., shown as a chevron shape extending into the second corecavity 504) the geometry, shape, orientation, etc. of the first cavitywall 512 can be varied without departing from the scope of the presentdisclosure. For example, in some alternative arrangements, the firstcavity wall may be arcuate or curved in a smooth transition from oneside of the airfoil to the other, with angled surfaces facing therespective exterior walls.

In addition to the first cavity wall 512 having angled surfaces 524,526, in some embodiments, the cavity impingement holes 520, 522 may beangled such that the air is forced to imping upon the exterior walls516, 518 of the second core cavity 508. After the air from the firstcore cavity 502 impinges upon the exterior walls 516, 518 at least aportion of the air will form a high momentum jet along the exteriorwalls 516, 518 and flow out of the second core cavity 504 through filmexits 528, 530. For example, air flowing through the first cavityimpingement hole 520 will contact the interior surface of the firstexterior wall 516 and run along the first exterior wall 516 to one ormore first film exits 528, where the air will exit the interior of theairfoil 500 and flow along and exterior surface of the airfoil 500(e.g., along a pressure side exterior surface). Similarly, air flowingthrough the second cavity impingement hole 522 will contact the interiorsurface of the second exterior wall 518 and run along the secondexterior wall 518 to one or more second film exits 530, where the airwill exit the interior of the airfoil 500 and flow along and exteriorsurface of the airfoil 500 (e.g., along a suction side exteriorsurface). The flow of the impingement air along the exterior walls 516,518 causes a dead zone to form within the middle of the second corecavity 504, as shown and described above.

As shown in FIG. 5B, impingement air 534 flows from the first corecavity 502 into the second core cavity 504 through the cavityimpingement holes 520, 522. The impingement air 534 divides into highmomentum jet air 536 that flows along the exterior walls 516, 518 and aradial cooling flow 538 within the second core cavity 504. The highmomentum jet air 536 is a film that flows along the exterior walls 516,518 and out through the film exits 528, 530 as film air 540 that willflow along an exterior surface of the airfoil 500 (e.g., within a hotgaspath). The radial cooling flow 538 will have a low momentum and/orvelocity within and around the dead zone (e.g., as shown in FIG. 4B)that is within the second core cavity 504. The radial cooling flow 538can form into a dynamic vortex within the second core cavity 504. Thatis, the radial cooling flow 538 portion of the impingement air 534 mayrotate within the dead zone of the cavity due to, in part, the highmomentum jet air 536. The dynamic vortex structure of the radiallycooling flow 538 may push the high momentum jet air 536 against theexterior walls 516, 518 and thus increase turbulence and, therefore,heat transfer within the second core cavity 504.

As shown in FIGS. 5A-5B, the airfoil 500 can include additional coolingcavities 532 located throughout the interior of the airfoil 500. Theadditional cooling cavities 532 can be parts of serpentine cavities,trailing edge cavities, flag tip cavities, or other cooling cavities(hybrid or non-hybrid (e.g., core) cavities).

Turning now to FIG. 6, a schematic illustration of a portion of anairfoil core structure 600 in accordance with an embodiment of thepresent disclosure is shown. The airfoil core structure 600 can be usedto manufacture airfoils in accordance with the present disclosure. Theairfoil core structure 600 includes a plurality of core bodies that arearranged to form cavities within an airfoil body (e.g., as shown anddescribed above). For example, the airfoil core structure 600 includestwo leading edge hybrid cavity cores 602, a first core cavity core 604,and a second core cavity core 606. The leading edge hybrid cavity cores602 are connected to the forward core cavity core 604 by one or moreforward impingement stems 608 that are arranged to form impingementholes between a formed first core cavity (from the first core cavitycore 604) and formed leading edge hybrid cavities (from the leading edgehybrid cavity cores 602). Similarly, one or more cavity impingementstems 610 connect the first core cavity core 604 with the second corecavity core 606 to form impingement holes between a formed first corecavity and a formed second core cavity, as shown and described above.

The first core cavity core 604 is arranged with a geometry to form afirst cavity wall of a formed second core cavity with a first surfaceand a second surface, as shown and described above. The first and secondsurfaces are arranged with the cavity impingement stems 610 to connectwith the second core cavity core 606. Extending from or attached to thesecond core cavity core 606 are one or more film exit stems 612 that arearranged to form the film exits as shown and described above. In someembodiments, rather than using stems 612, the film exits can be drilledholes.

Although the airfoil core structure 600 is shown with a specificarrangement and geometry, those of skill in the art will appreciate thatalternative arrangements are possible without departing from the scopeof the present disclosure. For example, in some embodiments, the filmexits can be formed using refractory metal core structures that areintegrally formed with or attached to the second core cavity core 606.Further, in some embodiments, manufacturing can be achieved usingadditive manufacturing techniques.

Turning now to FIG. 7, a schematic illustration of an airfoil 700 inaccordance with an embodiment of the present disclosure is shown. Theairfoil 700 includes a first core cavity 702 and a second core cavity704 having an arrangement similar to that described above, wherein sidecooling flows are generated by airflow that flows from the first corecavity 702 along interior side walls of the second core cavity 704 andthen is expelled out of the airfoil 700.

As shown, the interior of the airfoil 700, at a leading edge 706, isdivided into multiple leading edge hybrid cavities 708. The leading edgehybrid cavities 708 are arranged as leading-edge impingement cavitiesthat are supplied with impingement air from the first core cavity 702through one or more forward impingement holes 710. The leading edgehybrid cavities 708 are fed from the first core cavity 702, which may bea leading edge feed cavity which also feeds the second core cavity 704,in a manner similar to that described above.

The second core cavity 704 is defined in an axial direction between afirst cavity wall 712 and a second cavity wall 714. In a circumferentialdirection, the second core cavity 704 is defined by a first exteriorwall 716 and an opposing second exterior wall 718. As discussed above,the exterior walls 716, 718 of the second core cavity 704 are “hot”walls that are exposed to hot gaspath air, and the first cavity wall 712and the second cavity wall 714 are “cold” walls that are not exposed tothe hot gaspath air (i.e., they are internal walls). The first cavitywall 712 includes one or more cavity impingement holes 720, 722. A firstset of cavity impingement holes 720 is positioned and oriented withinthe first cavity wall 712 to direct an aft-flowing impingement flow fromthe first core cavity 702 into the second core cavity 704 and at thefirst exterior side wall 716. A second set of cavity impingement holes722 is positioned and oriented within the first cavity wall 712 todirect an aft-flowing impingement flow from the first core cavity 702into the second core cavity 704 and at the second exterior side wall718.

As shown, part of the directing of the impinging flow from the firstcore cavity 702 to the second core cavity 704 is achieved by the firstcavity wall 712 being contoured or shaped. In the present embodiment,the first cavity wall 712 has a first surface 724 that is angled orfaces the first exterior wall 716. Similarly, the first cavity wall 712has a second surface 726 that is angled or faces the second exteriorwall 718. In addition to the first cavity wall 712 having angledsurfaces 724, 726, in some embodiments, the cavity impingement holes720, 722 may be angled such that the air is forced to imping upon theexterior walls 716, 718 of the second core cavity 708. After the airfrom the first core cavity 702 impinges upon the exterior walls 716, 718at least a portion of the air will form a high momentum jet along theexterior walls 716, 718 and flow out of the second core cavity 704through film exits 728, 730. For example, air flowing through the firstcavity impingement hole 720 will contact the interior surface of thefirst exterior wall 716 and run along the first exterior wall 716 to oneor more first film exits 728, where the air will exit the interior ofthe airfoil 700 and flow along and exterior surface of the airfoil 700(e.g., along a pressure side exterior surface). Similarly, air flowingthrough the second cavity impingement hole 722 will contact the interiorsurface of the second exterior wall 718 and run along the secondexterior wall 718 to one or more second film exits 730, where the airwill exit the interior of the airfoil 700 and flow along and exteriorsurface of the airfoil 700 (e.g., along a suction side exteriorsurface). The flow of the impingement air along the exterior walls 716,718 causes a dead zone to form within the middle of the second corecavity 704, as shown and described above.

In the airfoil 700 shown in FIG. 7, the first cavity wall 712 and thesecond cavity wall 714 each include a central ridge. For example, asshown, a forward central ridge 742 is formed as part of or integral withthe first cavity wall 712. The forward central ridge extends aftwardinto the second core cavity 704 toward the second cavity wall 714.Similarly, an aft central ridge 744 is formed as part of or integralwith the second cavity wall 714. The aft central ridge 744 extendsforward into the second core cavity 704 toward the first cavity wall712. The central ridges 742, 744 do not extend entirely across thesecond core cavity 704, but rather are arranged to partially define atwo-vortex chamber within the second core cavity 704. That is, thecentral ridges 742, 744 are arranged to aid in the formation of thedynamic vortices within the radial cooling flow that passes or flowswithin the second core cavity. Further, the addition of the centralridges 742, 744 enables separation of two separate dynamic vorticeswithin the second core cavity.

Turning now to FIG. 8, a schematic illustration of a portion of anairfoil core structure 800 in accordance with an embodiment of thepresent disclosure is shown. The airfoil core structure 8 can be used tomanufacture airfoils in accordance with the present disclosure. Theairfoil core structure 800 includes two leading edge hybrid cavity cores802, a first core cavity core 804, and a second core cavity core 806.The leading edge hybrid cavity cores 802 are connected to the forwardcore cavity core 804 by one or more forward impingement stems 808 thatare arranged to form impingement holes between a formed first corecavity (from the first core cavity core 804) and formed leading edgehybrid cavities (from the leading edge hybrid cavity cores 802).Similarly, one or more cavity impingement stems 810 connect the firstcore cavity core 804 with the second core cavity core 806 to formimpingement holes between a formed first core cavity and a formed secondcore cavity, as shown and described above.

The first core cavity core 804 is arranged with a geometry to form afirst cavity wall of a formed second core cavity with a first surfaceand a second surface, as shown and described above. The first and secondsurfaces are arranged with the cavity impingement stems 810 to connectwith the second core cavity core 806. Extending from or attached to thesecond core cavity core 806 are one or more film exit stems 812 that arearranged to form the film exits as shown and described above. As shown,the second core cavity core 806 includes a forward central channel 814and an aft central channel 816 that are arranged to form forward and aftridges, respectively, as shown and described with respect to FIG. 7.

Although FIGS. 7-8 are illustrated with two central ridges (orassociated central channels in a core body), various embodiment may beformed alternatively. For example, in some embodiment, only one of theforward and second cavity walls may include the central ridge, ratherthan both of the forward and second cavity walls.

Turning now to FIG. 9, a schematic illustration of an airfoil 900 inaccordance with an embodiment of the present disclosure is shown. Theairfoil 900 includes a first core cavity 902 and a second core cavity904 having an arrangement similar to that described above, wherein sidecooling flows are generated by airflow that flows from the first corecavity 902 along interior side walls of the second core cavity 904 andthen is expelled out of the airfoil 900.

As shown, the interior of the airfoil 900, at a leading edge 906, isdivided into multiple leading edge hybrid cavities 908. The leading edgehybrid cavities 908 are arranged as leading-edge impingement cavitiesthat are supplied with impingement air from the first core cavity 902through one or more forward impingement holes 910. The leading edgehybrid cavities 908 are fed from the first core cavity 902, which may bea leading edge feed cavity which also feeds the second core cavity 904,in a manner similar to that described above.

The second core cavity 904 is defined in an axial direction between afirst cavity wall 912 and a second cavity wall 914. In a circumferentialdirection, the second core cavity 904 is defined by a first exteriorwall 916 and an opposing second exterior wall 918. As discussed above,the exterior walls 916, 918 of the second core cavity 904 are “hot”walls that are exposed to hot gaspath air, and the first cavity wall 912and the second cavity wall 914 are “cold” walls that are not exposed tothe hot gaspath air (i.e., they are internal walls). The first cavitywall 912 includes one or more cavity impingement holes 920, 922. A firstset of cavity impingement holes 920 is positioned and oriented withinthe first cavity wall 912 to direct an aft-flowing impingement flow fromthe first core cavity 902 into the second core cavity 904 and at thefirst exterior side wall 916. A second set of cavity impingement holes922 is positioned and oriented within the first cavity wall 912 todirect an aft-flowing impingement flow from the first core cavity 902into the second core cavity 904 and at the second exterior side wall918.

As shown, part of the directing of the impinging flow from the firstcore cavity 902 to the second core cavity 904 is achieved by the firstcavity wall 912 being contoured or shaped. In the present embodiment,the first cavity wall 912 has a first surface 924 that is angled orfaces the first exterior wall 916. Similarly, the first cavity wall 912has a second surface 926 that is angled or faces the second exteriorwall 918. In addition to the first cavity wall 912 having angledsurfaces 924, 926, in some embodiments, the cavity impingement holes920, 922 may be angled such that the air is forced to imping upon theexterior walls 916, 918 of the second core cavity 908. After the airfrom the first core cavity 902 impinges upon the exterior walls 916, 918at least a portion of the air will form a high momentum jet along theexterior walls 916, 918 and flow out of the second core cavity 904through film exits 928, 930. For example, air flowing through the firstcavity impingement hole 920 will contact the interior surface of thefirst exterior wall 916 and run along the first exterior wall 916 to oneor more first film exits 928, where the air will exit the interior ofthe airfoil 900 and flow along and exterior surface of the airfoil 900(e.g., along a pressure side exterior surface). Similarly, air flowingthrough the second cavity impingement hole 922 will contact the interiorsurface of the second exterior wall 918 and run along the secondexterior wall 918 to one or more second film exits 930, where the airwill exit the interior of the airfoil 900 and flow along and exteriorsurface of the airfoil 900 (e.g., along a suction side exteriorsurface). The flow of the impingement air along the exterior walls 916,918 causes a dead zone to form within the middle of the second corecavity 904, as shown and described above.

In the airfoil 900 shown in FIG. 9, the first and second film exits 928,930 are formed as circuit exits 946, 948, respectively. That is, inprior embodiments, as illustratively shown, the film exits have beenformed as film holes (e.g., discrete exits). However, in thisembodiment, an exit gap or channel can be formed, and in someembodiments, heat transfer augmentation features 946 a, 946 b, 948 a,948 b can be provided along the length of the film exits 928, 930 priorto exiting the airfoil. The heat transfer augmentation features 946 a,946 b, 948 a, 948 b can be pedestals, tear drops, racetracks, or othertypes of heat transfer augmentation features as appreciated by those ofskill in the art. Further, such increased size film exits 928, 930 canallow for more of the impinged air (e.g., side cooling flows) to flowdirectly along the side walls and provided cooling thereto, whilereducing an amount of cold air in the vortexes within the second corecavity 904.

Turning now to FIG. 10, a schematic illustration of a portion of anairfoil core structure 1000 in accordance with an embodiment of thepresent disclosure is shown. The airfoil core structure 1000 can be usedto manufacture airfoils in accordance with the present disclosure. Theairfoil core structure 1000 includes two leading edge hybrid cavitycores 1002, a first core cavity core 1004, and a second core cavity core1006. The leading edge hybrid cavity cores 1002 are connected to theforward core cavity core 1004 by one or more forward impingement stems1008 that are arranged to form impingement holes between a formed firstcore cavity (from the first core cavity core 1004) and formed leadingedge hybrid cavities (from the leading edge hybrid cavity cores 1002).Similarly, one or more cavity impingement stems 1010 connect the firstcore cavity core 1004 with the second core cavity core 1006 to formimpingement holes between a formed first core cavity and a formed secondcore cavity, as shown and described above.

The first core cavity core 1004 is arranged with a geometry to form afirst cavity wall of a formed second core cavity with a first surfaceand a second surface, as shown and described above. The first and secondsurfaces are arranged with the cavity impingement stems 1010 to connectwith the second core cavity core 1006. Extending from or attached to thesecond core cavity core 1006 are one or more film exit cores 1016 thatare arranged to form the film exits as shown and described above withrespect to FIG. 9. For example, as shown, the film exit core 1016includes first and second heat transfer augmentation core features 1016a, 1016 b to form various heat transfer augmentation features within afilm exit (e.g., film exits 928, 930 shown in FIG. 9). The film exitcore 1016, as shown, also defines a continuous structure for forming anexit line or gap that will be formed on an exterior surface of a formedairfoil.

Turning now to FIG. 11, a schematic illustration of an airfoil 1100 inaccordance with an embodiment of the present disclosure is shown. Theairfoil 1100 includes a first core cavity 1102 and a second core cavity1104 having an arrangement similar to that described above, wherein sidecooling flows are generated by airflow that flows from the first corecavity 1102 along interior side walls of the second core cavity 1104 andthen is expelled out of the airfoil 1100.

As shown, the interior of the airfoil 1100, at a leading edge 1106, isdivided into multiple leading edge hybrid cavities 1108. The leadingedge hybrid cavities 1108 are arranged as leading-edge impingementcavities that are supplied with impingement air from the first corecavity 1102 through one or more forward impingement holes 1110. Theleading edge hybrid cavities 1108 are fed from the first core cavity1102, which may be a leading edge feed cavity which also feeds thesecond core cavity 1104, in a manner similar to that described above.

The second core cavity 1104 is defined in an axial direction between afirst cavity wall 1112 and a second cavity wall 1114. In acircumferential direction, the second core cavity 1104 is defined by afirst exterior wall 1116 and an opposing second exterior wall 1118. Asdiscussed above, the exterior walls 1116, 1118 of the second core cavity1104 are “hot” walls that are exposed to hot gaspath air, and the firstcavity wall 1112 and the second cavity wall 1114 are “cold” walls thatare not exposed to the hot gaspath air (i.e., they are internal walls).The first cavity wall 1112 includes one or more cavity impingement holes1120, 1122. A first set of cavity impingement holes 1120 is positionedand oriented within the first cavity wall 1112 to direct an aft-flowingimpingement flow from the first core cavity 1102 into the second corecavity 1104 and at the first exterior side wall 1116. A second set ofcavity impingement holes 1122 is positioned and oriented within thefirst cavity wall 1112 to direct an aft-flowing impingement flow fromthe first core cavity 1102 into the second core cavity 1104 and at thesecond exterior side wall 1118.

As shown, part of the directing of the impinging flow from the firstcore cavity 1102 to the second core cavity 1104 is achieved by the firstcavity wall 1112 being contoured or shaped. In the present embodiment,the first cavity wall 1112 has a first surface 1124 that is angled orfaces the first exterior wall 1116. Similarly, the first cavity wall1112 has a second surface 1126 that is angled or faces the secondexterior wall 1118. In addition to the first cavity wall 1112 havingangled surfaces 1124, 1126, in some embodiments, the cavity impingementholes 1120, 1122 may be angled such that the air is forced to impingupon the exterior walls 1116, 1118 of the second core cavity 1108. Afterthe air from the first core cavity 1102 impinges upon the exterior walls1116, 1118 at least a portion of the air will form a high momentum jetalong the exterior walls 1116, 1118 and flow out of the second corecavity 1104 through film exits 1128, 1130. For example, air flowingthrough the first cavity impingement hole 1120 will contact the interiorsurface of the first exterior wall 1116 and run along the first exteriorwall 1116 to one or more first film exits 1128, where the air will exitthe interior of the airfoil 1100 and flow along and exterior surface ofthe airfoil 1100 (e.g., along a pressure side exterior surface).Similarly, air flowing through the second cavity impingement hole 1122will contact the interior surface of the second exterior wall 1118 andrun along the second exterior wall 1118 to one or more second film exits1130, where the air will exit the interior of the airfoil 1100 and flowalong and exterior surface of the airfoil 1100 (e.g., along a suctionside exterior surface). The flow of the impingement air along theexterior walls 1116, 1118 causes a dead zone to form within the middleof the second core cavity 1104, as shown and described above.

In the airfoil 1100 shown in FIG. 11, the first and second film exits1128, 1130 include funneling features 1150, 1152 formed in the secondcavity wall 1114 and along the side walls 1116, 1118. The funnelingfeatures 1150, 1152 are axial extensions of the second core cavity 1104that extend along the side walls 1116, 1118. The funneling features1150, 1152 enable funneling of more air to the film exits 1128, 1130,respectively, as compared to embodiments without such features, and canreduce the size of the dynamic vortices within the second core cavity1104.

Turning now to FIG. 12, a schematic illustration of a portion of anairfoil core structure 1200 in accordance with an embodiment of thepresent disclosure is shown. The airfoil core structure 1200 can be usedto manufacture airfoils in accordance with the present disclosure. Theairfoil core structure 1200 includes two leading edge hybrid cavitycores 1202, a first core cavity core 1204, and a second core cavity core1206. The leading edge hybrid cavity cores 1202 are connected to theforward core cavity core 1204 by one or more forward impingement stems1208 that are arranged to form impingement holes between a formed firstcore cavity (from the first core cavity core 1204) and formed leadingedge hybrid cavities (from the leading edge hybrid cavity cores 1202).Similarly, one or more cavity impingement stems 1210 connect the firstcore cavity core 1204 with the second core cavity core 1206 to formimpingement holes between a formed first core cavity and a formed secondcore cavity, as shown and described above.

The first core cavity core 1204 is arranged with a geometry to form afirst cavity wall of a formed second core cavity with a first surfaceand a second surface, as shown and described above. The first and secondsurfaces are arranged with the cavity impingement stems 1210 to connectwith the second core cavity core 1206. Extending from and integral withthe second core cavity core 1206 are funnel feature extensions 1218 thatare arranged to form funneling features as shown and described withrespect to FIG. 11. To core structure 1200 further includes one or morefilm exit stems 1212 that are arranged to form the film exits as shownand described above. The film exit stems 1212 extend from the funnelfeature extensions 1218.

Turning now to FIG. 13, a schematic illustration of a portion of anairfoil 1300. The portion shown in FIG. 13 is of an exterior wall 1318with a first cavity wall 1312 extending therefrom into an interior ofthe airfoil. The first cavity wall 1312 is substantially similar to thatshown and described above and is arranged to separate a first corecavity from a second core cavity. As shown, the first cavity wall 1312includes a plurality of cavity impingement holes 1322, with the firstcavity wall 1312 having a surface 1326 that is angled toward an interiorsurface 1354 of the exterior side wall 1318. Although in someembodiments, the cavity impingement holes may be circular “holes” othergeometries for such impingement passages are possible. For example, inthis embodiment, the cavity impingement holes 1322 have radiallyextending, oblong orientations. This geometry can result in theimpingement air being distributed radially along the interior surface1354 of the exterior side wall 1318. This arrangement can provide for asubstantial portion (or all) of the interior surface 1354 to receiveimpingement air from a first core cavity. As shown, to achieve theorientation shown in FIG. 13, the cavity impingement holes 1322 have anaxis 1356 that runs parallel to the radial direction of the airfoil1300.

Turning now to FIG. 14, a schematic illustration of a portion of anairfoil 1400. The portion shown in FIG. 14 is of an exterior wall 1418with a first cavity wall 1412 extending therefrom into an interior ofthe airfoil. The first cavity wall 1412 is substantially similar to thatshown and described above and is arranged to separate a first corecavity from a second core cavity. As shown, the first cavity wall 1412includes a plurality of cavity impingement holes 1422, with the firstcavity wall 1412 having a surface 1426 that is angled toward an interiorsurface 1454 of the exterior side wall 1418. In this embodiment, thecavity impingement holes 1422 have axially extending, oblongorientations along the first cavity wall 1412. In this embodiment, thecavity impingement holes 1422 are axially lengthened such that theimpinged air on the interior surface 1454 of the exterior side wall 1418remains on the interior surface 1454 longer (e.g., in time) regardlessof augmentation features such as trip strips or small pin fins formed inor on the interior surface 1454 of the exterior side wall 1418. Asshown, to achieve the orientation shown in FIG. 14, the cavityimpingement holes 1422 have an axis 1456 that runs perpendicular to theradial direction of the airfoil 1400.

Although FIGS. 13-14 illustrate specific orientations of oblong cavityimpingement holes, various other orientations are possible withoutdeparting from the scope of the present disclosure. The orientation ofFIG. 13 can represent a zero degree angling of the cavity impingementholes relative to the exterior side wall and the orientation of FIG. 14can represent a 90° angling of the cavity impingement holes relative tothe exterior side wall. A 180° angling would appear as the arrangementshown in FIG. 13 (i.e., 0° and 180° appear the same due to the oblonggeometry and shape of the cavity impingement holes). In variousembodiments, the cavity impingement holes can take any degree of anglingrelative to the exterior side wall from 0° to 180°. That is, the cavityimpingement holes have oblong shapes with a long axis oriented between0° and 180° relative to the first exterior side wall.

Turning now to FIG. 15, a schematic illustration of an airfoil 1500 inaccordance with an embodiment of the present disclosure is shown. Theairfoil 1500 includes a first core cavity 1502 and a second core cavity1504 having an arrangement different from the above describedembodiments. In this embodiment, the first core cavity 1502 is locatedaft of the second core cavity 1504. However, similar to the abovedescribed embodiments, side cooling flows are generated by airflow thatflows from the first core cavity 1502 along interior side walls of thesecond core cavity 1504 and then is expelled out of the airfoil 1500.

As shown, the interior of the airfoil 1500, at a leading edge 1506, isdivided into multiple leading edge hybrid cavities 1508. The leadingedge hybrid cavities 1508 are arranged as leading-edge impingementcavities that are supplied with impingement air from a leading edge feedcavity 1558 through one or more forward impingement holes 1510. In thisembodiment, unlike that described above, the leading edge feed cavity1558 is not fluidly connected to either of the first or second corecavities 1502, 1504.

The first core cavity 1502, in this embodiment, is a conventional cavitythat can be sourced with cooling air from other cavities within theairfoil 1500 and/or from a cooling source that is located at an end ofthe airfoil body (e.g., at platform ends of a vane or at a root of ablade, depending on the configuration of the airfoil). The second corecavity 1504 is defined in an axial direction between a first cavity wall1512 and a second cavity wall 1514. In a circumferential direction, thesecond core cavity 1504 is defined by a first exterior wall 1516 and anopposing second exterior wall 1518. Similar to that described above, theexterior walls 1516, 1518 of the second core cavity 1504 are “hot” wallsthat are exposed to hot gaspath air, and the first cavity wall 1512 andthe second cavity wall 1514 are “cold” walls that are not exposed to thehot gaspath air (i.e., they are internal walls).

The first cavity wall 1512 includes one or more cavity impingement holes1520, 1522. A first set of cavity impingement holes 1520 is positionedand oriented within the first cavity wall 1512 to direct an aft-flowingimpingement flow from the first core cavity 1502 into the second corecavity 1504 and at the first exterior side wall 1516. A second set ofcavity impingement holes 1522 is positioned and oriented within thefirst cavity wall 1512 to direct an aft-flowing impingement flow fromthe first core cavity 1502 into the second core cavity 1504 and at thesecond exterior side wall 1518.

As shown, part of the directing of the impinging flow from the firstcore cavity 1502 to the second core cavity 1504 is achieved by the firstcavity wall 1512 being contoured or shaped. In the present embodiment,the first cavity wall 1512 has a first surface 1524 that is angled orfaces the first exterior wall 1516. Similarly, the first cavity wall1512 has a second surface 1526 that is angled or faces the secondexterior wall 1518. In addition to the first cavity wall 1512 havingangled surfaces 1524, 1526, in some embodiments, the cavity impingementholes 1520, 1522 may be angled such that the air is forced to impingupon the exterior walls 1516, 1518 of the second core cavity 1508. Afterthe air from the first core cavity 1502 impinges upon the exterior walls1516, 1518 at least a portion of the air will form a high momentum jetalong the exterior walls 1516, 1518 and flow out of the second corecavity 1504 through film exits 1528, 1530.

For example, air flowing through the first cavity impingement hole 1520will contact the interior surface of the first exterior wall 1516 andrun in a forward direction along the first exterior wall 1516 to one ormore first film exits 1528, where the air will turn and exit theinterior of the airfoil 1500 and flow along and exterior surface of theairfoil 1500 (e.g., along a pressure side exterior surface). Similarly,air flowing through the second cavity impingement hole 1522 will contactthe interior surface of the second exterior wall 1518 and run in forwarddirection along the second exterior wall 1518 to one or more second filmexits 1530, where the air will exit the interior of the airfoil 1500 andflow along and exterior surface of the airfoil 1500 (e.g., along asuction side exterior surface). The flow of the impingement air alongthe interior surface of the exterior walls 1516, 1518 within the secondcore cavity 1504 causes a dead zone to form within the middle of thesecond core cavity 1504.

Turning now to FIG. 16, a schematic illustration of a portion of anairfoil core structure 1600 in accordance with an embodiment of thepresent disclosure is shown. The airfoil core structure 1600 can be usedto manufacture airfoils in accordance with the present disclosure. Theairfoil core structure 1600 includes two leading edge hybrid cavitycores 1602 and a leading edge feed cavity core 1603. Further, theairfoil core structure 1600 includes a first core cavity core 1604 and asecond core cavity core 1606, arranged to form fluidly connected firstand second core cavities. The leading edge hybrid cavity cores 1602 areconnected to the leading edge feed cavity core 1604 by one or moreforward impingement stems 1608 that are arranged to form impingementholes between a formed leading edge feed cavity and formed leading edgehybrid cavities. In contrast to the previously discussed embodiments,one or more cavity impingement stems 1610 connect the first core cavitycore 1604 with the second core cavity core 1606 to form impingementholes between a formed first core cavity and a formed second corecavity.

The first core cavity core 1604 is arranged with a geometry to form afirst cavity wall of a formed second core cavity with a first surfaceand a second surface, as shown and described above. The first and secondsurfaces are arranged with the cavity impingement stems 1610 to connectwith the second core cavity core 1606. Extending from and integral withthe second core cavity core 1606 one or more film exit stems 1612 thatare arranged to form the film exits as shown and described above.

In the above shown embodiments, the cavity impingement holes of theimpingement wall are shown as misaligned in the radial direction. Thatis, the cavity impingement holes in one angled surface of the firstcavity wall are located at a different radial position than the cavityimpingement holes in the other angled surface of the first cavity wall.This arrangement is shown, for example, in the arrangement shown in theairfoil core structures of FIGS. 6, 8, 10, 12, and 16. In theseillustrations, the cavity impingement stems in one surface are notaligned in the radial direction with the cavity impingement stems of theother surface. In contrast, the cross-sectional illustrations of FIGS.5A, 7, 9, 11, and 15, the cavity impingement holes are shown at the sameradial position (i.e., shown in the cross-sectional slice of therespective airfoils)

Accordingly, in some embodiments, the cavity impingement holes of theimpingement wall can be aligned between the two surfaces and in otherembodiments, the cavity impingement holes may be misaligned in theradial direction. For example, when aligned, the impinging air flowingthrough a first cavity impingement hole in a first surface of theimpingement wall can impact the first exterior wall at the same airfoilradial position (e.g., height within the airfoil) as the impinging airflowing through a second cavity impingement hole in a second surface ofthe impingement wall and impinging upon the second exterior wall. Thatis, the arrays of cavity impingement holes can have an aligned pattern.However, in other embodiments, radial staggering, misalignment, oroffset of the impingement holes within the two surfaces of theimpingement wall may be employed. The arrangement of the cavityimpingement holes (e.g., staggered or aligned) may alter the nature ofthe dynamic vortices within the second core cavity. For example, analigned configuration may result in a stable or relatively linearseparation between the two vortices. In contrast, a staggeredarrangement may result in a wavy or possibly turbulent interactionbetween neighboring dynamic vortices. Accordingly, vortex pressures mayvary depending on the arrangement and configuration and/or angle oforientation and may result in different hot wall cooling streambehavior.

Turning to FIG. 17, a schematic illustration of a first cavity wall 1712having a plurality of cavity impingement holes 1720, 1722 is shown. Afirst set of cavity impingement holes 1720 is shown formed in a firstangled surface 1724 of the first cavity wall 1712 and a second set ofcavity impingement holes 1722 is shown formed in a second angled surface1726 of the first cavity wall 1712. As illustratively shown, theimpingement holes of the first set of cavity impingement holes 1720 arealigned in a radial direction with the impingement holes of the secondset of cavity impingement holes 1722.

Turning to FIG. 18, a schematic illustration of a first cavity wall 1812having a plurality of cavity impingement holes 1820, 1822 is shown. Afirst set of cavity impingement holes 1820 is shown formed in a firstangled surface 1824 of the first cavity wall 1812 and a second set ofcavity impingement holes 1822 is shown formed in a second angled surface1826 of the first cavity wall 1812. As illustratively shown, theimpingement holes of the first set of cavity impingement holes 1820 areoffset in a radial direction from the impingement holes of the secondset of cavity impingement holes 1822.

Turning now to FIG. 19, a schematic illustration of an airfoil corestructure 1900 in accordance with an embodiment of the presentdisclosure is shown. The airfoil core structure 1900 can be used tomanufacture airfoils in accordance with the present disclosure. Theairfoil core structure 1900 includes two leading edge hybrid cavitycores 1902, a first core cavity core 1904 (forming, in part, a leadingedge feed cavity core), and a second core cavity core 1906, arranged toform fluidly connected first and second core cavities. The leading edgehybrid cavity cores 1902 are connected to the leading edge feed cavitycore 1904 by one or more radially aligned forward impingement stems 1908a, 1908 b that are arranged to form aligned impingement holes in aradial direction between a formed leading edge feed cavity and formedleading edge hybrid cavities. The aligned forward impingement stems 1908a, 1908 b are arranged to form aligned impingement holes, e.g.,impingement holes located at similar radial positions, for each of theleading edge hybrid cavities. Similarly, one or more aligned (in aradial direction) cavity impingement stems 1910 a, 1910 b connect thefirst core cavity core 1904 with the second core cavity core 1906 toform radially aligned impingement holes between a formed first corecavity and a formed second core cavity that are aligned at radialpositions in a formed airfoil. This arrangement is in contrast to thestructures of the airfoil core structures of FIGS. 6, 8, 10, and 12,which all shown unaligned or offset forward impingement stems andunaligned or offset cavity impingement stems.

Although the various above embodiments are shown as separateillustrations, those of skill in the art will appreciate that thevarious features can be combined, mix, and matched to form an airfoilhaving a desired cooling scheme that is enabled by one or more featuresdescribed herein. Thus, the above described embodiments are not intendedto be distinct arrangements and structures of airfoils and/or corestructures, but rather are provided as separate embodiments for clarityand ease of explanation.

Advantageously, embodiments provided herein are directed to airfoilcooling cavity structures that combine the benefits of hybrid cavitiesand traditional core cavities. Further, advantageously, improved partlife, improved cooling, and reduced weight can all be achieved fromembodiments of the present disclosure.

As used herein, the term “about” is intended to include the degree oferror associated with measurement of the particular quantity based uponthe equipment available at the time of filing the application. Forexample, “about” may include a range of ±8%, or 5%, or 2% of a givenvalue or other percentage change as will be appreciated by those ofskill in the art for the particular measurement and/or dimensionsreferred to herein.

The terminology used herein is for the purpose of describing particularembodiments only and is not intended to be limiting of the presentdisclosure. As used herein, the singular forms “a,” “an,” and “the” areintended to include the plural forms as well, unless the context clearlyindicates otherwise. It will be further understood that the terms“comprises” and/or “comprising,” when used in this specification,specify the presence of stated features, integers, steps, operations,elements, and/or components, but do not preclude the presence oraddition of one or more other features, integers, steps, operations,element components, and/or groups thereof. It should be appreciated thatrelative positional terms such as “forward,” “aft,” “upper,” “lower,”“above,” “below,” “radial,” “axial,” “circumferential,” and the like arewith reference to normal operational attitude and should not beconsidered otherwise limiting.

While the present disclosure has been described with reference to anillustrative embodiment or embodiments, it will be understood by thoseskilled in the art that various changes may be made and equivalents maybe substituted for elements thereof without departing from the scope ofthe present disclosure. In addition, many modifications may be made toadapt a particular situation or material to the teachings of the presentdisclosure without departing from the essential scope thereof.Therefore, it is intended that the present disclosure not be limited tothe particular embodiment disclosed as the best mode contemplated forcarrying out this present disclosure, but that the present disclosurewill include all embodiments falling within the scope of the claims.

What is claimed is:
 1. An airfoil for a gas turbine engine, the airfoilcomprising: an airfoil body having a plurality of cavities formedtherein, the airfoil extending in a radial direction between a first endand a second end, and extending in an axial direction between a leadingedge and a trailing edge; a first core cavity within the airfoil body,the first core cavity being one of the plurality of cavities formed inthe airfoil body; a second core cavity located within the airfoil bodyand adjacent the first core cavity, wherein the second core cavity isdefined by a first cavity wall, a second cavity wall opposing the firstcavity wall, a first exterior wall, and a second exterior wall opposingthe first exterior wall, wherein the first cavity wall is locatedbetween the second core cavity and the first core cavity and the firstand second exterior walls are exterior walls of the airfoil body, thesecond core cavity being another of the plurality of cavities formed inthe airfoil body; wherein the first cavity wall includes a first surfaceangled toward the first exterior wall and a second surface angled towardthe second exterior wall; at least one first cavity impingement holeformed within the first surface, wherein a first impingement flow flowsfrom the first core cavity through the at least one first cavityimpingement hole and impinges upon the first exterior wall to form afirst high momentum jet of impingement air thereon; at least one secondcavity impingement hole formed within the second surface, wherein asecond impingement flow flows from the first core cavity through the atleast one second cavity impingement hole and impinges upon the secondexterior wall to form a second high momentum jet thereon; and a forwardcentral ridge extending into the second core cavity from the firstcavity wall, an aft central ridge extending into the second core cavityfrom the second cavity wall, wherein the forward central ridge and theaft central ridge at least partially divide the second core cavity intoa two-vortex chamber.
 2. The airfoil of claim 1, wherein the firstimpingement flow separates into the first high momentum jet flowingalong the first exterior wall and a first portion of a radial coolingflow within the second core cavity and the second impingement flowseparates into the second high momentum jet flowing along the secondexterior wall and a second portion of the radial cooling flow within thesecond core cavity, wherein the first and second portions of the radialcooling flow flow radially within the two-vortex chamber.
 3. The airfoilof claim 1, further comprising at least one circuit exit in the firstexterior wall, the at least one circuit exit arranged to expel air fromthe second core cavity through the first exterior wall.
 4. The airfoilof claim 3, further comprising a funneling feature extending from thesecond core cavity along the first exterior wall to the at least onecircuit exit.
 5. The airfoil of claim 3, further comprising at least oneheat transfer augmentation feature within the at least one circuit exit.6. The airfoil of claim 1, further comprising at least one film exit inthe first exterior wall, the at least one film exit arranged to expelair from the second core cavity through the first exterior wall.
 7. Theairfoil of claim 6, further comprising a funneling feature extendingfrom the second core cavity along the first exterior wall to the atleast one film exit.
 8. The airfoil of claim 1, wherein the at least onefirst cavity impingement hole has one of a radial orientation in theradial direction, an axial orientation in the axial direction, or anangular orientation relative to at least one of the radial direction andthe axial direction within the first cavity wall.
 9. A gas turbineengine comprising: an airfoil having an airfoil body having a pluralityof cavities formed therein, the airfoil extending in a radial directionbetween a first end and a second end, and extending axially between aleading edge and a trailing edge; a first core cavity within the airfoilbody, the first core cavity being one of the plurality of cavitiesformed in the airfoil body; a second core cavity located within theairfoil body and adjacent the first core cavity, wherein the second corecavity is defined by a first cavity wall, a second cavity wall opposingthe first cavity wall, a first exterior wall, and a second exterior wallopposing the first exterior wall, wherein the first cavity wall islocated between the second core cavity and the first core cavity and thefirst and second exterior walls are exterior walls of the airfoil body,the second core cavity being another of the plurality of cavities formedin the airfoil body; wherein the first cavity wall includes a firstsurface angled toward the first exterior wall and a second surfaceangled toward the second exterior wall; at least one first cavityimpingement hole formed within the first surface, wherein a firstimpingement flow flows from the first core cavity through the at leastone first cavity impingement hole and impinges upon the first exteriorwall to form a first high momentum jet of impingement air thereon; atleast one second cavity impingement hole formed within the secondsurface, wherein a second impingement flow flows from the first corecavity through the at least one second cavity impingement hole andimpinges upon the second exterior wall to form a second high momentumjet thereon; and a forward central ridge extending into the second corecavity from the first cavity wall, an after central ridge extending intothe second core cavity from the second cavity wall, wherein the forwardcentral ridge and the aft central ridge at least partially divide thesecond core cavity into a two-vortex chamber.
 10. The gas turbine engineof claim 9, wherein the first impingement flow separates into the firsthigh momentum jet flowing along the first exterior wall and a firstportion of a radial cooling flow within the second core cavity and thesecond impingement flow separates into the second high momentum jetflowing along the second exterior wall and a second portion of theradial cooling flow within the second core cavity, wherein the first andsecond portions of the radial cooling flow flow radially within thetwo-vortex chamber.
 11. The gas turbine engine of claim 9, furthercomprising at least one circuit exit in the first exterior wall, the atleast one circuit exit arranged to expel air from the second core cavitythrough the first exterior wall.
 12. The gas turbine engine of claim 11,further comprising a funneling feature extending from the second corecavity along the first exterior wall to the at least one circuit exit.13. The gas turbine engine of claim 11, further comprising at least oneheat transfer augmentation feature within the at least one circuit exit.14. The gas turbine engine of claim 9, further comprising at least onefilm exit in the first exterior wall, the at least one film exitarranged to expel air from the second core cavity through the firstexterior wall.
 15. The gas turbine engine of claim 14, furthercomprising a funneling feature extending from the second core cavityalong the first exterior wall to the at least one film exit.
 16. The gasturbine engine of claim 9, wherein the at least one first cavityimpingement hole has one of a radial orientation in the radialdirection, an axial orientation in an axial direction, or an angularorientation relative to at least one of the radial direction and theaxial direction within the first cavity wall.